A composite construction, such as, in particular, a composite plate having a sandwich-type construction, has two outer layers which are mutually opposed in parallel and a foam material completely filling the space between the outer layers at least in some regions. The outer layers are interconnected by means of spacers, and the spacers are connected to the outer layers via a cured plastics material.

A radome includes a first layer through which electromagnetic radiation is transmittable. The radome also includes a moisture barrier layer connected to the second layer, the moisture barrier layer being formed of a single sheet of polychlorotrifluoroethene or a liquid crystal polymer.

ABTRACT

The present invention relates to a liquid, thermoplastic acrylic gel cap composition that can impart UV resistance, higher impact, and aesthetic effects to a composite material. Additionally, the post processing of the material when combined with a thermoplastic composite can allow for thermoformability, weldability and recyclability, unlike seen with traditional thermoset based gel coats.

A multiaxial textile fabric has at least two thread layers and at least one nonwoven layer. Each thread layer is made of multifilament reinforcement yarns arranged parallel to one another and so as to lie adjacently next to one another within the thread layers, wherein at least one thread layer is at least partially directly contacted by the nonwoven layer, and cut-out sections are provided within the nonwoven layer, the cut-out sections having a size of at least 4 mm.sup.2. The multiaxial textile fabric also includes a fiber-reinforced composite material.

Processes for forming composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

Production process of a composite product (1) comprising a core (2), a first layer (3) comprising a sheet impregnated with a solid polyurethane material, and a polymer-based film (7) applied to the first layer (3), wherein the process comprises: producing a semi-finished product comprising the core (2) and the sheet impregnated by a liquid mixture precursor of the solid polyurethane material; adhering the film (7) to a first half-mould (11) by applying a depression between the film (7) and the half-mould (11); pressing two half-moulds (11, 12) against each other with the semi-finished product interposed between two shaping surfaces (13), so that the film (7) comes into contact with the liquid mixture; with the semi-finished product in the mould, thermosetting the liquid mixture to transform it into the polyurethane solid material so that the film (7) firmly adheres to the first layer (3) and thus producing the composite product (1).

A high-pressure tank comprises a liner, a strengthening layer including a first helical layer and a first hoop layer each including a carbon fiber, and a protective layer including a second helical layer and a second hoop layer each including a glass fiber, in this order. The high-pressure tank is provided with a stress-generating portion, a reinforcement layer includes a first area α overlapping the stress-generating portion in a stacking direction and a second area β that is an area except for the first area, and a one-round portion including a final crossing portion at an end of winding of the glass fiber constituting the second hoop layer overlaps the second area in the stacking direction.

Methods for manufacturing composite components having complex geometries are provided. In one exemplary aspect, a method includes laying up each of a plurality of laminates to an initial shape with a substantially planar geometry or a gently curved geometry. Then, a laid up laminate is formed to a final shape for each predefined section defined by the composite component to be manufactured. Thereafter, the laminates formed to their respective final shapes are stacked to build up the complex geometry of the composite component. Next, the composite component can be cured and finish machined as necessary to form the completed composite component.

The invention relates to a method for the manufacture of a leak-tight vessel comprising a cylindrical mantle and two dome-shaped ends for the storage of a gas and/or a liquid. The method comprises providing an inner barrier layer comprising a heat-sealable thermoplastic material and an outer shell layer comprising a fiber-reinforced heat-sealable thermoplastic material, as well as an end-fitting. Further, the method comprises providing an inner layer by winding a heat-sealable thermoplastic filament material and forming an outer layer in two steps: first providing around the mantle of the vessel a fabric of a fiber-reinforced heat-sealable material, whereby the width of the fabric diminishes with successive windings of the fabric around the mantle, followed by winding a fiber-reinforced heat-sealable plastic film over the fabric around the mantle and the dome-shaped endings.

A method for forming a resin-based composite structure is provided. The method includes: providing a prepreg layup, wherein the prepreg layup includes an epoxy resin-carbon fiber composite material; covering a thermal-fusion material on a surface of the prepreg layup; and performing a molding and curing process to fuse the thermal-fusion material with the prepreg layup. Wherein the molding and curing process includes: heating at a first temperature to melt, soften and fully fuse the thermal-fusion material with the prepreg layup; and heating at a second temperature to solidify the thermal-fusion material for forming the resin-based composite structure. Wherein the first temperature is lower than the second temperature.